Radiator for aeroplanes.



W. L. GILMORE (II W. E. VALK, JR.

RADIATOR FOR AEROPLANES.

APPLICATION FILED NOV 16. I9II.

Patented M31. 11, 1919.

F165 avwemtoz WILLIAM L. GILMORE AND WILLIAM E. VALK, J R., 013 BUFFALO, NEW YORK, ASSIGNORS TO OURTISS AEROP LAIN E AND MOTOR CORPORATION, A CORPORATION OF NEW YORK.

RADIATOR'FOR AEROPLANES.

11.29%, TOO.

Specification of Letters Patent. Patented Mar. 11, 1919..

Application filed November 16, 1917. Serial No. 202,428.

propelling power plants and more particu-.

larly to radiators for water cooled aeronautical motors of the internal combustion type.

It has been the practice heretofore in the design of an aeroplane to locate the radiair rush.

ator of the propelling power plant either at the extreme forward end of the fuselage or at the sides thereof, or possibly directly beneath the supporting surface or surfaces according to whether the craft is of the pusher or tractor type. If the radiator is located at the nose end of the fuselage (the conventional location) all possibility of obtaining a good streamline is eliminated.

For a good streamline the entering portion,

of any body must be rounded and blunt. If it is located elsewhere either the streamline of the fuselage is interrupted or the radiator itself set apart in the direct line of Since it is impracticable to streamline a radiator in its present form, its resistance to forward flight is enormous.

The one big advantage-of the present types of radiators is the dependable and efficient cooling effect aflorded upon .the cooling agent by reason of the direct exposure of the radiator cells or sections to the air.

The characteristic of this invention is the construction oftheradiator in such manner I thatit is translated throiigh theair edgewise and with a minimum of resistance. The radiator is itself of substantially aerofoil section and mounted either within or in direct continuation of the supporting surface or surfaces. It comprises in its preferred embodiment a plurality of longitu-.

dinally extending radiator sections having spacers mounted between them to provide air passages whereby the radiating surface of the radiator is increased. Headers are mounted at the ends of the radiator sections and are connected with the motor by suit ablevconnections. ,An expansion tank may or may not be' rovided. The construction of the radiator 1n aerofoil form is distinctly. advantageous in that a certain amount of 7 motor to stall.

- lift is obtained by reason of its placement within or in continuation of the wings.

Moreover, the standard wing section is such that that portion of the radiator of maximum depth or thickness lies substantially coincident withthe center of lift of the wings.

Another characteristic of the invention is the use of a shutter or slide beneath the radiator to increase or diminish the effective area thereof should occasion demand. It is a known fact that in high altitudes the cooling efficiency of a radiator is increased to such an extent as to oftentimes cause the With this adjustable slide or shutter such a contingency is avoided. As the machine climbs the effective area of the radiator may be decreased So that the temperature of the cooling agent is held more'or less constant. Furthermore, as the effective area of the radiator is decreased the total wing surface is proportionately increased and the lift augmented. The details of the invention such as the construction of the various radiator parts will be hereinafter more particularly pointed out.

Of the drawings: 1

Figure l, is a front end elevation of a portion of the upper supporting surface of a biplane s owing its preferred location with respect to the fuselage or body and the relative location of the radiator.

Fig. 2, is a longitudinal sectional view showing the radiator construction and its arrangement between the Wing beams of the supporting surface.

' This supporting surface extends intermediately across the body 10 and is preferably I of a standard construction or rather curvature in cross section. It comprises the usual front wing beam 11, rear wing beam 12, nose strip 13, trailing edge strip 14 and ribs 15,

the latter being preferably alined between the nose strip and the front wing beam, the

two wing beams, and the rear wing beam and the trailing edge strip respectively. The radiator designated as an entirety by the numeral 16 is preferably constructed in duplicate radiator units arranged respectively symmetrically at opposite sides of the longitudinal vertical plane of the fore and aft axis of the machine. These sections or units are interconnected as at 17' and connected with the motor (not shown) by suitable piping or other connections. Each radiator unit comprises a plurality of parallel radiator sections 17 of substantially aerofoil form. These sections are spaced apart uniformly by partitions or spacers 18 which are inclined preferably rearwardly and upwardly from the underneath surface of the radiator. The radiator sections are further provided with transverse air passages 19 which lighten them and increase their radiating surface. Headers 20- are mounted at the ends of the radiator unit-s and are fastened in any suitable manner to the win beams 11 and 12. The radiator sections 1 are of a duplicate construction and so related to the win or supporting surface as to constitute in e-tl e ct an integral part thereof. The connection 17 between the radiator units are inclosed within the wing structure as are the radiator units themselves. The arrangement of the radiator units is accordingly such as to ofier a minimum of resistance and at the same time some if not considerable lift by reason of the aerofoil form gii'en the sections of which the radiator units are composed. \Ve thus convert into an element afiording useful lift that which heretofore has offered resistance only. The

radiator by its placement is translated through the air edgewise and efiectually streamlined. The section of the radiator of maximum thickness (which is in continuation of the corresponding section of the supporting surface) is also approximately alined with the normal center of ressure or lift. This arrangement is desira le in that a maximum of air is brought into contact with that portion of the radiator of maximum radiation surface.

As an element of safety the radiator is provided with an expansion tank 22 of streamline form. This tank is mounted preferably above the plane of the wing surface and connected as at 23 with the headers 20. Expansion of the cooling agent is thus taken care of should it reach a boiling point or its temperature be increased sufficiently to cause the agent to expand. The tank 22 is equipped with a filler plug 24.

The spacers 18 it will be noted are inclined in the direction of the air flow caused by the partial elimination of the air pressure ordinarily created beneath an aerofoil surface. This is desirable in that the resistance is to some extent reduced. The spacers are preferably constructed of thin sheet metal, flanged as at 25 and 26 and brazed on to the side walls of the radiator sections 17. The details of the spacer construction will be seen in Figs. 4 and 5. The headers 20 areof course, open to the several radiator sectionsto provide for circulation of the cooling agent from the forward end of the radiator rearwardly to the sections to the outlet end at the rear.

By the placement of the radiator units at opposite sides of the fore and aft axis of the tween the radiator sections.

Each unit of the radiator is further provided with a. shutter or slide 27 movable longitudinally of the wings. These shutters 27 are .to be manipulated by any suitable means from the cockpit of the craft to either increaseor decrease the effective area of the radiator according to the needs of the motor.

.In extremely cold weather or in high altitudes the shutters 27 are slid inwardly to cover a portion of the radiator surface ordinarily efle'ctive to thus simultaneously decrease the cooling eflect and increase the lifting efficiency of the wings by reason of. the increased supporting surface area. The shutters preferably underlie that portion of the wing surface remote from the fuselage to work inwardly so that the radiator sec tion directly adj.cent the fuselage will be the last section covered. Obviously as the wing surfaces approach the fuselage an appreciable decrease in-lift is caused by the interference of the fuselage with the flow of air. Guides 28 overlap the fore and aft edges of the shutters which are curved or cambered slightly to complement the wings.

It is to be'understood that thebasic idea here involved is the construction of the radiator insubstantially aerofoil form or in a form substantially horizontally flat for translation through the air edgewise to offer a minimum of resistance without decreased cooling efficiency. The radiator may of course, be made as a unit and placed directly above the fuselage, or in fact at any point within either supporting surface. It may be extended beyond the wing beams of the wings, or it may be extended slightly above the plane of the top surface of the wing without departing from the spirit of the invention claimed. In other words it is to be understood that no limitation is intended ator for aeroplanes comprising a plurality of radiator sections ofsubstantially aerofoil form together with means for directing the air stream over the side walls of the radiator sections when the radiator is translated edge- Wise through the air.

2. A substantially horizontally fiat radiator for aeroplanes of approximately aerofoil form together With means movable relatively to it for regulating the air flow through the radiator parts, the radiator, by reason of its construction exerting some useful lift, the extent of the lift being "ariable by adjustment of said movable means.

3. A substantially horizontally flat radiator for aeroplanes of approximately aerofoil form in combination with means movable relatively to it for simultaneously lessening the radiating efficiency of the radiator and increasing the dynamic lift or vice versa.

4. A radiator for aeroplanes comprising a plurality of spaced radiator sections of substantially aerofoil form havingair passages extending transversely through' them, the ends of the air passages being open to the air space between the radiator sections.

5. A radiator for aeroplanes comprising a plurality of laterally spaced longitudinally extending radiator sections having transverse air passages formed in them together with means between the sections arranged to provide upwardly and rearwardly inclined air passages.

6. A radiator for aeroplanes comprising a plurality of laterally spaced longitudinally extending radiator sections of substantially aerofoil form (viewed from the-side), the arrangement of the sections being such that air is permitted to pass transversely between them withoutnullifying completely the dynamic lift efficiency of the radiator as a whole.

7. The combination with a radiator for aeroplanes of'substantially aerofoil form, of means for regulating the quantity of air passing through it.

8. Aradiator for aeroplanes comprising a plurality of longitudinally extending radiator sections having spacers arranged between them to extend angularly upwardly and rearwardly.

9. A radiator for aeroplanes comprising a plurality of longitudinally extending radiator sections of substantially aerofoil form,

headers common to the several sections,

transverse air passages formed in said sections, and spacers arranged between said sections for holding them in parallelism. I

10. A radiator for aeroplanes comprising a plurality of laterallyspaced longitudinally extending radiator sections, transversely ex-. tended headers common to the several sections, and spacers providing air passages between said sections.

- 11. A radiator for aeroplanes comprising a plurality of radiator sections of substan- 13. A radiator for aeroplanes comprising longitudinally separated headers, radiator sections interconnecting the headers, and an expansion tank common to both headers.

14. In an aircraft, the combination with a supporting surface, of a radiator of substantially aerofoil section mounted in continuation of said surface without interrupting the continuity of the structural elements thereof, the said radiator comprising a plurality of radiator sections appropriately spaced to increase the effective radiation surface.

15. In an aircraft, the combination with a supporting surface, of a radiator built into saidsurface as an integralpart thereof and in a manner such that air is 'permittedjto pass transversely through 'th ,suppQrtiv-fig surface to increase the cooling. etficiency of the radiator. q I

16. In an aircraft, the combinationwith a supporting surface, of a radiator of substantially aerofoil section built into said surfaoe, said radiator comprising a-- plurality of laterally spaced radiator sections, the exterior lines of which are such that the continuity of the exterior surface of the supporting surface is uninterrupted throughout.

17. In an aircraft, the combination with a supporting surface, of a radiator of substan-' tially aerofoil section mounted in continuation of said surface with its section of maximum thickness coincident with the center of pressure of said surface.

18. In an aircraft, the combinationwith a supporting surface, of a radiator of substantially aerofoil form built into an opening in the supporting surface to continue the exterior form of said surface uninterruptedly,

together with means for varying the size of said opening to cut down the effective area of the radiator and simultaneously increase the lifting efficiency of the supporting surface-or vice versa.

19. In an aircraft, the combination with a supporting surface, of a radiator of substantially aerofoil form mounted in an opening formed in said supporting surface, and

means for varying the effective area of the radiator by alterin the size of said opening.

' 20. In an aircra ,the combination with a supporting surface, of a radiator of substantially aerofoil section mounted 1n continuation of said surface with its area of maximum radiation substantially coincident with the center of the pressure thereof.

21. In an aircraft, the combination with a fuselage having aeroplane wings extended laterally from it in the plane of the top thereof, of radiators mounted in said wings closely adjacent the fuselage, the placement of the radiators being such that the air ordinarily confined within the angles formed between the fuselage and wings will escape through the radiators.

22. In an aircraft, the combination with a supporting surface, a radiator built into said surface, and means for varying the effective area of the radiator to either increase 'or decrease the lifting efficiency of said surface.

23. A radiator forairplanes of substantially aerofoil section having air passages extending transversely through it, the air passages being generally inclined rearwardly p and upwardly from the underneath face of.

tending air passages formed hit, the arrangement of the air passages being such that air is forced through them as the radiator is translated bodily edgewise through the air, said radiator from front to rear being generally inclined to present, during'its translation through the air, an angle of incidence conducive to some useful lift.

In testimony whereof we hereunto aifix our signatures.

WILLIAM L. GILMORE. WILLIAM E. VALK, JR. 

